Fuel flow control

ABSTRACT

A fuel flow control system is configured to perform a method including: setting a fuel flow demand proportional to compressor discharge pressure; detecting an actual fuel flow; and applying an enhanced schedule for fuel flow demand while fuel flow demand is less than a predefined proportion of actual fuel flow.

BACKGROUND

The present disclosure concerns a method of controlling fuel flow in agas turbine engine. It also concerns a fuel flow control system and afuel flow system for a gas turbine engine, which implement the method.

In a gas turbine engine it is conventional to control the fuel flow viaa series of control laws. The amount of fuel flow may be determined by afunction which is dependent on an engine shaft speed, a pressure ratioor a combination of these parameters. It may also be modulated by otherfactors such as altitude, for a gas turbine engine powering an aircraft.The fuel flow may be controlled to open loop, without feedback as towhether the instructed fuel flow has resulted in the desired enginespeed change, or closed loop, with feedback.

Typically there are maximum and minimum fuel flow limiters whichoverride the fuel flow control laws to ensure the engine is neitherstarved of fuel nor over-fuelled and hence flooded or caused to runaway.

One problem with relying on the normal fuel flow control laws occurswhen a gas turbine engine surges. In a surge the compressor dischargepressure drops rapidly regardless of the amount of fuel supplied to theengine. There is thus a danger of over-fuelling the engine during asurge. It is known to apply a surge control law so that fuel flow demandis pegged to the compressor discharge pressure, that is it isproportional to compressor discharge pressure, as it drops fromdetection of a surge condition. FIG. 2 shows this behaviour. The lineN_(L_D) shows the unaltered speed demand for an exemplary one of theengine shafts and line N_(L_A) is the actual speed of the shaft. A surgeoccurs at approximately time 0.3. The line P₃₀ shows the compressordischarge pressure which drops rapidly following the surge event. Theline W_(f_D) shows the demanded fuel flow which has a small increase asthe actual shaft speed N_(L_A) drops as the control laws try to returnthe actual shaft speed N_(L_A) to the demanded shaft speed N_(L_D). Thenthe demanded fuel flow W_(f_D) drops away tracking the reduction incompressor discharge pressure P₃₀. The line is stepped due to the timeconstant of the applicable control law. The actual fuel flow W_(f_A)tracks the demanded fuel flow W_(f_D) with a lag.

When the compressor discharge pressure P₃₀ begins to recover, atapproximately time 0.6, the demanded fuel flow W_(f_D) also begins toincrease. The surge is recovered where the compressor discharge pressureP₃₀ and actual shaft speed N_(L_A) plateau, since at this level theactual fuel flow W_(f_A) is sufficient to sustain the current actualshaft speed N_(L_A). However, because the fuel flow demand W_(f_D) islower than the actual fuel flow W_(f_A) the fuel flow continues toreduce and thus the recovered engine continues to decelerate.

The increase in demanded fuel flow W_(f_D) is limited by a maximum ratelimiter and so the increase in fuel flow, and consequently the arrestingof the actual shaft speed N_(L_A) decrease, is slow. Indeed, asillustrated the demanded and actual fuel flow W_(f_D), W_(f_A) have onlyrecovered to around 30% of their maximum values by time 1.4 when thespeed demand N_(L_D) is significantly reduced whereas before the surge,at the left hand side of FIG. 2, the demanded and actual fuel flowsW_(f_D), W_(f_A) were over 90% of their maximum values.

SUMMARY

A disadvantage of the known method of controlling fuel flow during andfollowing an engine surge is that the fuel flow demand W_(f_D) isheavily depressed by tracking compressor discharge pressure P₃₀ and isslow to recover to pre-surge levels.

According to a first aspect there is provided a method of controllingfuel flow in a gas turbine engine, the method comprising steps to:

-   -   a) detect a surge condition;    -   b) set fuel flow demand proportional to compressor discharge        pressure;    -   c) detect actual fuel flow; and    -   d) apply an enhanced schedule for fuel flow demand while fuel        flow demand is less than a predefined proportion of actual fuel        flow.

Advantageously the method recovers fuel flow demand more quickly after asurge than known methods.

The method may comprise a further step to revert to normal fuel flowcontrol laws once fuel flow demand equals or exceeds the predefinedproportion of actual fuel flow. Advantageously the method only appliesduring surge and recovery.

Step c) may precede or occur in parallel to step b).

The method may comprise a step to apply a second enhanced schedule forfuel flow demand while fuel flow demand is less than a second predefinedproportion of actual fuel flow demand; wherein the second predefinedproportion is smaller than the predefined proportion. Advantageouslythis permits the fuel flow demand to recover to the actual fuel flow intwo stages to reduce the likelihood of surge recurring.

The predefined proportion may be in the range 0.5 to 1.5. The predefinedproportion may be in the range 0.5 to 1. The predefined proportion maybe in the range 0.75 to 1. The second predefined proportion may be inthe range 0.5 to 1.5. The second predefined proportion may be in therange 0.5 to 1. The second predefined proportion may be in the range0.75 to 1.

The enhanced schedule may comprise a high rate of increase of fuel flowdemand. The enhanced schedule may comprise the maximum of a) an enhancedrate of increase defined by the predefined proportion multiplied by theactual fuel flow minus the demanded fuel flow, divided by a time stepand b) the normal rate of fuel flow increase. The enhanced schedule maycomprise the sum of a) the predefined proportion multiplied by theactual fuel flow, and b) one minus the predefined proportion multipliedby the demanded fuel flow. Advantageously each of these embodiments ofthe enhanced schedule accelerates recovery following an engine surge.

The enhanced schedule may be limited by a maximum rate of change of fuelflow demand. This may reflect physical constraints of the system, forexample valve slew rates, or may reduce the possibility of a recurrenceof the surge.

The second enhanced schedule may comprise a higher rate of increase offuel flow demand than the enhanced schedule. Advantageously the initialrecovery of fuel flow demand from surge is rapid and then the rate slowsas the fuel flow demand nears the actual fuel flow to reduce thelikelihood of overshoot.

The actual fuel flow may be measured by a position of a fuel meteringvalve.

The present invention also provides a fuel flow control systemconfigured to perform the method as described, and a fuel flow systemcomprising such a fuel flow control system. The present invention alsoprovides a gas turbine engine comprising such a fuel flow controlsystem, and a gas turbine engine comprising such a fuel flow system.

The skilled person will appreciate that except where mutually exclusive,a feature described in relation to any one of the above aspects may beapplied mutatis mutandis to any other aspect. Furthermore except wheremutually exclusive any feature described herein may be applied to anyaspect and/or combined with any other feature described herein.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments will now be described by way of example only, with referenceto the Figures, in which:

FIG. 1 is a sectional side view of a gas turbine engine;

FIG. 2 is a graph of parameters during surge under conventional fuelflow control laws;

FIG. 3 is a schematic of a fuel flow control system;

FIG. 4 is a flow chart of the method of the present invention;

FIG. 5 is a plot of the manner in which an enhanced fuel flow demandschedule acts;

FIG. 6 is a plot of an enhanced fuel flow demand schedule;

FIG. 7 is a graph of parameters during surge using the enhanced fuelflow demand schedule of FIG. 6;

FIG. 8 is a graph of parameters during surge using another enhanced fuelflow demand schedule;

FIG. 9 is a block diagram of an exemplary control arrangement.

DETAILED DESCRIPTION OF EMBODIMENTS

With reference to FIG. 1, a gas turbine engine is generally indicated at10, having a principal and rotational axis 11. The engine 10 comprises,in axial flow series, an air intake 12, a propulsive fan 13, anintermediate pressure compressor 14, a high-pressure compressor 15,combustion equipment 16, a high-pressure turbine 17, an intermediatepressure turbine 18, a low-pressure turbine 19 and an exhaust nozzle 20.A nacelle 21 generally surrounds the engine 10 and defines both theintake 12 and the exhaust nozzle 20.

The gas turbine engine 10 works in the conventional manner so that airentering the intake 12 is accelerated by the fan 13 to produce two airflows: a first air flow into the intermediate pressure compressor 14 anda second air flow which passes through a bypass duct 22 to providepropulsive thrust. The intermediate pressure compressor 14 compressesthe air flow directed into it before delivering that air to the highpressure compressor 15 where further compression takes place.

The compressed air exhausted from the high-pressure compressor 15 isdirected into the combustion equipment 16 where it is mixed with fueland the mixture combusted. The resultant hot combustion products thenexpand through, and thereby drive the high, intermediate andlow-pressure turbines 17, 18, 19 before being exhausted through thenozzle 20 to provide additional propulsive thrust. The high 17,intermediate 18 and low 19 pressure turbines drive respectively the highpressure compressor 15, intermediate pressure compressor 14 and fan 13,each by suitable interconnecting shaft.

Other gas turbine engines to which the present disclosure may be appliedmay have alternative configurations. By way of example such engines mayhave an alternative number of interconnecting shafts (e.g. two) and/oran alternative number of compressors and/or turbines. Further the enginemay comprise a gearbox provided in the drive train from a turbine to acompressor and/or fan.

A fuel flow system 68 is illustrated schematically in FIG. 3. Fuel issupplied to the gas turbine engine 10 from one or more fuel tanks 70,for example located in the aircraft body or wings where the gas turbineengine 10 powers an aircraft. The fuel may be pressurised through one ormore pumps 72 and delivered to a fuel metering valve 74. The fuelmetering valve 74 is controlled by a fuel flow control system 76 whichimplements methods of controlling the fuel flow in the gas turbineengine 10. The fuel metering valve 74 delivers the demanded fuel flow tothe combustor 16, via one or more sets of fuel injectors.

A method 30 of controlling fuel flow in a gas turbine engine 10 isdescribed with respect to FIG. 4. The method 30 may be implemented inthe fuel flow control system 76. The method 30 acts in response to asurge condition 32. Optionally a pre-step to detect the surge condition32 by any conventional method may be implemented in the method 30. Forexample, surge may be detected from a rapid reduction in compressordischarge pressure P₃₀. Alternatively the surge condition 32 need not bedetected since the method 30 reacts to the effects of the surge withoutrequiring explicit detection of the surge condition 32.

In step 34 of the method 30 the fuel flow demand W_(f_D) is set to beproportional to the compressor discharge pressure P₃₀. The relationshipbetween fuel flow demand W_(f_D) and compressor discharge pressure P₃₀may be linear, with a constant of proportionality, or may be non-linear.The relationship between fuel flow demand W_(f_D) and compressordischarge pressure P₃₀ may be defined by the maximum flow limiter forthe fuel flow control system. An exemplary maximum flow limit iscalculated as the compressor discharge pressure P₃₀ multiplied by aconstant. The constant may itself be a function of engine speed.

Also in response to the surge condition 32 the current actual fuel flowW_(f_A) is detected, step 36. This step may occur before, during orafter step 34 in which the fuel flow demand W_(f_D) is set proportionalto compressor discharge pressure P₃₀.

Step 38 is a comparison step. The actual fuel flow W_(f_A) is multipliedby a predefined proportion k. The predefined proportion k may be aconstant. It may be in the range 0.5 to 1. The demanded fuel flowW_(f_D) is then compared to the product of the predefined proportion kand the actual fuel flow W_(f_A). If the demanded fuel flow W_(f_D) isless than the product of the predefined proportion k and the actual fuelflow W_(f_A), thus W_(f_D)<k·W_(f_A), then an enhanced fuel flow demandschedule is applied at step 40. Conversely, if the demanded fuel flowW_(f_D) is greater than or equal to the product of the predefinedproportion k and the actual fuel flow W_(f_A), thus W_(f_D)≥k·W_(f_A),then the normal fuel flow control laws set the demand schedule, step 42.

Where the enhanced fuel flow demand schedule is applied, step 40, aniteration loop 44 ensures that the method 30 is repeated until theoutcome of the comparison at step 38 returns the fuel flow demandschedule to the normal control laws, step 42.

The enhanced fuel flow demand schedule applied at step 40 of the method30 provides a step increase to the fuel flow demand W_(f_D).Advantageously this allows the fuel flow demand W_(f_D), and thus theactual fuel flow W_(f_A), to recover to the pre-surge levels morequickly than in the known control methods. The maximum (and minimum)fuel flow limiters remain in operation throughout control of the fuelflow by the method 30. Therefore one or both of the limiters mayoverride the fuel flow demand W_(f_D) generated by the enhanced fuelflow schedule if it is too aggressive for the engine conditions.

FIG. 5 is a schematic plot of the effect of applying the enhanced fuelflow demand schedule at step 40. At the time at which the maximum fuelflow limiter based on compressor discharge pressure P₃₀ is no longer thecontrolling control law, the fuel flow demand W_(f_D) is the level 45shown. The actual fuel flow W_(f_A) is higher and is shown by the dashedhorizontal line. FIG. 5 is a simplified plot since, as seen in FIG. 2,the actual fuel flow W_(f_A) continues to fall whilst the fuel flowdemand W_(f_D) is lower than the actual fuel flow W_(f_A) and so thedashed line should have a downward trend.

In a first embodiment the enhanced fuel flow demand schedule applies arate accelerator 46 to the fuel flow demand W_(f_D) to rapidly increasethe fuel flow demand W_(f_D) to the level of the actual fuel flowW_(f_A). The first embodiment is described in more detail with respectto FIG. 6. In second and third embodiments the enhanced fuel flow demandschedule applies a step change to the fuel flow demand W_(f_D), as shownby line 48, to a predefined proportion k of the actual fuel flowW_(f_A). The predefined proportion k may be less than one, asillustrated. Alternatively the predefined proportion k may be equal toone, in which case the fuel flow demand W_(f_D) steps directly to theactual fuel flow W_(f_A). In a further alternative the predefinedproportion k may be greater than one, in which case the fuel flow demandW_(f_D) steps above the actual fuel flow W_(f_A) and therefore has agreater effect on surge recovery.

The larger the predefined proportion k, the quicker the surge recovery.However, the smaller the predefined proportion k, the more robust andstable the surge recovery. Therefore it is beneficial to set thepredefined proportion k to a value that suitably balances the speed andstability of surge recovery for the particular application of the method30.

The first embodiment of the enhanced fuel flow demand schedule 50 isshown in FIG. 6. The x-axis represents the ratio of fuel flow demandW_(f_D) to actual fuel flow W_(f_A). The y-axis represents the rate ofchange of fuel flow demand W_(f_D) ^(•) which is applied to theunderlying fuel flow demand W_(f_D) due to its relationship tocompressor discharge pressure P₃₀. The rate of change of fuel flowdemand W_(f_D) ^(•) is normalised by division by the fuel flow demandW_(f_D), thus W_(f_D) ^(•)/W_(f_D), which is a fuel flow rate limiter.When the ratio is below a first threshold R₁ a high rate of increase offuel flow demand W_(f_D) ^(•) is applied to the fuel flow demand W_(f_D)at each time step. This is shown by the section of the fuel flow demandschedule 50 which is labelled 52.

When the ratio shown on the x-axis is between the first threshold R₁ anda second, higher threshold R₂ a different rate of increase of fuel flowdemand W_(f_D) ^(•) is applied to the fuel flow demand W_(f_D) at eachtime step. This is the section labelled 54. The rate of increase betweenthe thresholds R₁, R₂ may be a transitional rate of increase of fuelflow demand W_(f_D) such that the rate is inversely proportional to themagnitude of the ratio. When the ratio is above the second threshold R₂there may be a further rate of increase of fuel flow demand W_(f_D) ^(•)applied. The further rate of increase may correspond to the normal fuelflow control laws. This is section 56 of the fuel flow demand schedule50 shown in FIG. 6.

The first threshold R₁ may be in the range 0 to 0.7, for example around0.5. Thus when the fuel flow demand W_(f_D) is less than half of theactual fuel flow W_(f_A) the high rate of increase 52 of fuel flowdemand W_(f_D) ^(•) is applied. The second threshold R₂ may be in therange 0.5 to 1, for example around 0.7 to 0.85. Thus when the fuel flowdemand W_(f_D) is 50% to 85% of the actual fuel flow W_(f_A) thetransitional rate of increase 54 of fuel flow demand W_(f_D) ^(•) isapplied. The high and transitional rates of increase 52, 54 may be, forexample, expressed as slew rates for a mechanical fuel metering valve.

The effect of the first embodiment of the fuel flow demand schedule 50can be seen in FIG. 7. The dotted lines correspond to the lines in FIG.2. The fuel flow demand W_(f_D) is modified in that it begins to risemore quickly than when controlled by the normal fuel flow control laws.The vertical distance between the fuel flow demand W_(f_D) and theactual fuel flow W_(f_A) is the ratio. At the time indicated by dashedline 58 the vertical distance between the fuel flow demand W_(f_D) andthe actual fuel flow W_(f_A) is less than or equal to the firstthreshold R₁. Thus the fuel flow demand W_(f_D) is approximately 35% ofthe actual fuel flow W_(f_A). At the time indicated by dashed line 60the vertical distance between the fuel flow demand W_(f_D) and theactual fuel flow W_(f_A) is equal to the second threshold R₂. Thus thefuel flow demand W_(f_D) is approximately 80% of the actual fuel flowW_(f_A).

During the time interval marked by double-headed arrows 62 thetransitional rate 54 of increase of fuel flow demand W_(f_D) is appliedby the enhanced fuel flow demand schedule 50. After time 60 the normalcontrol laws are applied, for example comprising an exponential rate ofincrease of fuel flow demand W_(f_D). The increase in fuel flow demandW_(f_D) causes a consequential, lagged increase in the actual fuel flowW_(f_A). This is shown in FIG. 7. Advantageously the fuel flow demandW_(f_D) grows more rapidly than in the conventional situation where theenhanced demand schedule 50 is not applied because the base fuel flowdemand W_(f_D), to which the exponential rate of fuel flow demandincrease W_(f_D) ^(•) (normal control laws) is applied, is higher.

Advantageously the effect of the enhanced fuel flow demand schedule 50is that the fuel flow demand W_(f_D) is driven to track the compressordischarge pressure P₃₀ not only as it reduces following a surge eventbut also as it rises rapidly as the engine 10 recovers from the surgecondition 32.

A second embodiment of the enhanced fuel flow demand schedule 50 has asingle threshold ratio R₃. The schedule 50 is arranged to calculate thefuel flow demand W_(f_D) necessary to match the threshold ratio R₃ ofthe fuel flow demand W_(f_D) to the actual fuel flow W_(f_A). Thethreshold R₃ may be, for example, 0.85. The threshold R₃ is chosen sothat the fuel flow demand W_(f_D) does not fall below this proportion ofthe actual fuel flow W_(f_A) during normal rapid engine decelerationsbut only falls below the proportion during surge events. Recovery fromsurge is quicker the closer the threshold R₃ is to one.

Where the fuel flow demand W_(f_D) is greater than or equal to thethreshold R₃ multiplied by the actual fuel flow W_(f_A), thusW_(f_D)≥R₃·W_(f_A), the rate of increase of fuel flow demand W_(f_D)^(•) from the normal control laws is applied. As in the firstembodiment, this rate W_(f_D) ^(•) may be exponential.

Where the fuel flow demand W_(f_D) is less than the predefinedproportion k multiplied by the actual fuel flow (for example0.85·W_(f_A)) the second embodiment of the enhanced fuel flow demandschedule 50 performs a calculation, compares it to the fuel flow rateW_(f_D) ^(•) from the normal control laws, and applies the larger value.The calculation is the difference between the product of the thresholdratio R₃ and the actual fuel flow W_(f_A), R₃·W_(f_A), and the fuel flowdemand W_(f_D). The difference is then divided by the controller timestep being the time step in which updated control instructions can beimplemented. The predefined proportion k is the proportion of the actualfuel flow W_(f_A) to which it is desired that the fuel flow demandW_(f_D) steps, as shown by line 48 in FIG. 5. Thus the calculation is:

$\frac{{R_{3} \cdot W_{{f\;\_\; A}\;}} - W_{f\mspace{11mu}\_\; D}}{timestep}.$Alternatively the calculation is the difference between the actual fuelflow W_(f_A) and the fuel flow demand W_(f_D), multiplied by thethreshold ratio R₃ and divided by the time step:

$\frac{R_{3}\left( {W_{{f\;\_\; A}\;} - W_{f\mspace{11mu}\_\; D}} \right)}{timestep}.$The enhanced fuel flow demand schedule 50 applies this calculated ratewhen the fuel flow demand W_(f_D) is less than the predeterminedproportion k of the actual fuel flow W_(f_A) unless the normal fuel flowcontrol laws give a larger rate of increase W_(f_D) ^(•).

In a third embodiment of the enhanced fuel flow demand schedule 50 thefuel flow demand W_(f_D) is set to be a sum of two components: onerelated to the actual fuel flow W_(f_A) and one related to the fuel flowdemand W_(f_D). A constant n is multiplied by the actual fuel flowW_(f_A) to give the first component, nW_(f_A). One minus the constant nis multiplied by the fuel flow demand W_(f_D) to give the secondcomponent, (1−n)·W_(f_D). The constant n may be, for example, in therange 0.25 to 1.25 inclusive. By changing the value of the constant nthe speed and robustness of the recovery of the engine 10 from the surgeevent can be optimised. Since the constant n is selected to be aroundunity it biases the schedule 50 to have more influence from the actualfuel flow W_(f_A) than the fuel flow demand W_(f_D). As can be seen inFIG. 8 the actual fuel flow W_(f_A) is considerably larger than the fuelflow demand W_(f_D) within a short time after the surge event, whichoccurs around time 0.3, and so this bias forces the fuel flow demandW_(f_D) to rise quickly. Once the maximum fuel flow limiter is no longerlimiting the fuel flow demand W_(f_D) the normal control laws take overcontrol of the fuel flow demand W_(f_D), for example applying anexponential rate of increase W_(f_D) ^(•).

A block diagram of an example implementation of the third embodiment isshown in FIG. 9.

Advantageously the third embodiment of the enhanced fuel flow demandschedule 50 applies a more aggressive increase in fuel flow demandW_(f_D), from the nadir of the compressor discharge pressure P₃₀, thanthe first embodiment and so the base fuel flow demand W_(f_D) to whichthe normal, exponential, rate of increase W_(f_D) ^(•) is applied ishigher. Thus the fuel flow demand W_(f_D) recovers to its pre-surgelevel more rapidly than the first embodiment and much more rapidly thanthe conventional method in which no enhanced schedule 50 was applied.

Advantageously the third embodiment of the enhanced fuel flow demandschedule 50 does not require a step of determining if the ratio of fuelflow demand W_(f_D) up to actual fuel flow W_(f_A) is less than athreshold ratio before applying the enhanced schedule 50. Instead thecalculation can be operational throughout fuel flow control but willonly control the fuel flow demand W_(f_D) up in response to a surgecondition 32 and when the maximum fuel flow rate limiter based oncompressor discharge pressure P₃₀ stops being in control of the fuelflow. Optionally a step to determine if the fuel flow demand W_(f_D) isless than a threshold ratio R of the actual fuel flow W_(f_A) may beused to trigger application of the third embodiment of the enhanced fuelflow demand schedule 50.

Although the method 30 is most accurate when the actual fuel flowW_(f_A) can be measured at step 36, for example from the physicalposition of the fuel metering valve 74, the method 30 can also beimplemented by using a simulated value of actual fuel flow W_(f_A). Sucha simulated value may be derived from a model of the dynamic response ofthe fuel flow system 68.

Advantageously the method 30 enables other methods to be applied in anengine control system which have an adverse effect on surge recovery.For example some methods to detect and/or accommodate shaft breakevents, which have some similar characteristics to surge events, havethe effect of degrading surge recovery. The method 30 described hereinovercomes that degraded surge recovery and so makes use of both methodsfeasible.

The method 30 is also applicable to marine and industrial gas turbineengines.

It will be understood that the invention is not limited to theembodiments above-described and various modifications and improvementscan be made without departing from the concepts described herein. Exceptwhere mutually exclusive, any of the features may be employed separatelyor in combination with any other features and the disclosure extends toand includes all combinations and sub-combinations of one or morefeatures described herein.

What is claimed is:
 1. A controller configured to control a fuelmetering valve by performing the following: a. in response to a detectedsurge condition that occurs while controlling the fuel flow according tofuel control laws, setting a fuel flow demand (Wf_D) proportional tocompressor discharge pressure (P₃₀), such that the fuel flow demand(Wf_D) varies with varying compressor discharge pressure (P₃₀); b.detecting actual fuel flow (Wf_A); and c. applying a rate accelerator ora step change to the fuel flow demand (Wf_D), which was previously setin response to the detected surge condition, to provide a first rate ofincrease of the fuel flow demand (Wf_D), while the fuel flow demand(Wf_D) is less than a predefined proportion (k) of the actual fuel flow(Wf_A), the first rate of increase being greater than a rate of increasethat would have occurred in response to the detected surge conditionunder the fuel control laws that were being used prior to setting thefuel flow demand (Wf_D) proportional to the compressor dischargepressure (P₃₀).
 2. A gas turbine engine comprising: a combustor; a fuelmetering valve that controls fuel flow to the combustor; and thecontroller as claimed in claim 1, operatively connected to the fuelmetering valve.